Multilayered and FGM structural elements under mechanical and thermal loads. Part I: Comparison of finite elements and analytical models

• Finite element analysis of composite structures.
• Deformation of a layered exhaust pipe covered by thermal barrier coating subjected to internal pressure and temperature gradient.
• Deformation of a two-layered plate under thermal loading.
• Deflections of three-layered beams subjected to bending with non-symmetrical cross-section.

Nowadays modern composites with various internal structures are used for manufacturing of structural parts of airplanes and in other branches of engineering. They have a layered structure or can be produced as functionally graded materials (FGM). For specific applications some porosity is necessary to satisfy technological process requirements.In this paper several numerical models of structural parts of airplanes made of different composites were elaborated. The finite element (FE) analysis and the mechanical response of the structural elements were compared with previously formulated simplified analytical models [1] and [2]. The calculations concern estimation of deformation states in:–a layered exhaust pipe covered by thermal barrier coating (TBC) subjected to an internal pressure and a temperature gradient,–a two-layered plate under thermal loading,–three-layered beams subjected to bending with non-symmetrical cross-section,–a FGM beam element subjected to bending load,–a FGM two-layered rod subjected to uniaxial tension.For each considered case a good correlation of the results using both methods – analytical and numerical ones – was obtained, which proves correctness of the theoretical derivations, [1] and [2]. The paper provides also own general procedure for modelling of FGM in the ABAQUS.